apollo 10 briefing

8/7/2019 Apollo 10 Briefing

1/84

- A * /ca,. 'i - f

NA TIO NA L AERONAUTICS A N D SPACE ADMINISTRATION WO 2-4155WASHINGTON, D .C .20546 TELS W O 3-6925

FOR RELEASE: IMMEDIATEMonday, A p r i l 14, 1969

APOLLO i o BRIEFING

PARTICIPANTS:GEORGE H, HAGE, Deputy Apollo Program Director,NASA HeadquartersCOLONJ3L THOMAS McMIJLLEN, Assistant Mission DirectorWILLIAM J, O'DONWELL, Assistant Publ ic Affairs Officer ,OMSF, NASA


2/84

: Good afternoon^B e gin w i t h Q U ~ r i e f i n g , P would l i k e

a couple of announcements,F i r s t , there w i l l be pr in t ed t r ansc r ip t s p rov idedof t h e b r i e f i n g , If you are i n t e r e s t e d i n r e c ei v i ng one ofthese t r a n a c r i p t s , please address a government envelope w i t hyour own address. You w i l l f i n d t h e envelopes i n t h e lobby.The second announcement is t h a t a b r i e f i n g on t h e

NASA p o r t i o n of President Nixon*s amended f i s c a l 1970 Budgetw i l l be h e l d tomorrow, Tuesday, A p r i l 15, a t 5:OO p.m.,Eastern Standard T i m e , a t t h e NASA Headquarters Auditorium,s i x t h f loor , FOB 6, 400 Maryland Avenue, Southwest.To begin t h i s a f t e r n o o n ' s a c t i v i t i e s w e w i l l havet h e Apollo 10 mission b r i e f ing by Mr. George Hage, who ist h e Apollo Mission Director, also Deputy Director of t h eApollo Program.With M r , Hage is Colonel Tom McMullan, As s i s t an tMission Director.George.HAGE: Thank you,Ladies and gentlemen, we w i l l presen t t h e Apollo 10miss ion b r i e f ing today i n three par ts . I w i l l s t a r t it outw i t h a d i scus s ion of t h e mission up t o t h e p o i n t 09 rendez-vous, Colonel McMullen w i l l d i s c u s s t h e d e t a i l s of t h erendezvous. And I w i l l take t h e mission from t h a t po in t onback t o recovery.As many of you know, Apollo 10 is proceeding w e l ltowards a launch r ea d in e ss on May 18. The launch timeplanned is 11:49 a .m , , Eastern Standard Time,The f l i g h t r ea di ne ss test w a s succes s fu l ly com-p l e t e d on schedule l a s t Thursday, A p r i l 9,We hays t w o majar remaining events pr io r to ourl a ~ n c ~eadin ess s t a t us . General P h i l l i p s ' f l i g h t r sadi -ness re view w i l l be conducted at Kennedy on t h e 22nd of


3/84

t h i s month.t h e countdo

the 2nd ofth8 COUntd

to have the

items shown

The spacecraft lunar module adapter No, 13.Luminary pro of the t w o space-craft, res

~~~~C~ fro neh Complex39-I3,

u le Pilot,


4/84

cA

-3a-

e0mv)

8 -.-

004Ana

L,

n0QsW

2tdL=.-5J


5/84

z0U5zPL0E5v,z0U5We0z0wv,v)EU

W - -

0 - 0 a

-v)z0I--4=cr:wCL0I-SW

w

Vz3UJ


6/84

C h r i s Kraf( ind i ca t ing ) unde r theThe bs t i m e invo lve TaskForce 130 and he prime recovery s h i pbeing t h e USS a landing pad hel icopter ,

and g u i d e l i n e s fo r t h i s missionare summar mportant ones is t o l a y t h i smission ou e as t h e G missionor t h e f i r s t l u n a r l a n ~ i n ~i v e p o s s i b l e launck da ys across t h e e i g h t -$he 1 8 t h throug the 25th of May. I t w i l l be

t a r g e t e d to achie t f a v o r ab l e l i g h t i n g o n t h e primeAp01lo G Pan s 2, 3, 4 and 5.tter two days i n t h e missiongh t ing t o g ive t h e a d d i t i o n a lona l t w o days , t h e 24th androblem preven ts us from going*he 18th .

a y ~ i g ~ taunch and la nd in g and re-

on -- w i l l be ta rge ted fori t h an e a r t h r e t u r n pe r i -a low po in t o r perigee with

ar o r b i t i n j e c t i o n a sW e n t h e f i r s t o r b i t ,e ir 0 by 60 s i t u a t i o n .


7/84

-4a-

>--4wv)0dmU

(3Tz.ECBJ-3M

30c3 53).M53z

a0t-in05 5:iEw I

i53wwa

szOL3I--wEwwE

0 =b-e3:02L -OLwaaz0b- a a542a.aI0z3t-It3I r:s

p.z*w 4


8/84

Z3AUIII-dnn-ZQU


9/84

time and thethe 18th thlaunch. The earliesmentioned, the last opportunitybeing at 4: e a ~ t e r ~ ~ o ~f the 25th.~ ~ ~ ~ ws a function-t of Cape K ~ n n e ~ y *

f a t e d , thatB are shown here,gle between the sun

and the loc

m i ~ ~ i o n ~o ~ ~ o ~ t ~ n iy we have beention or higher lightingangle in or lity of going on that day.

(Slide)in a schematic way depictsopportunity for an S-IVBcauble with this pointer --f third orbit.

the generic ion. And we have launch


10/84

-5a-

v)P0.(19

aQ

za

t-

o za-

cu c) lo u)

0-0 'cu

7I

cc


11/84

-5b-

111.4LdCYa

h w.m m 0hb

lasuns

'Imas ! r u n s


12/84

-5c-

II


13/84

,E

-5d-

7nm0.0.t

I04s CVt\

a


14/84

-5e - Revision 2

I

W -1

17


15/84

6NOW, a f t e r t h e t r a n s l u n a r i n j e c t i o n bu rn , t h espacecraft prepare for t r a n s p o s i t i o n and docking. Thef i r s t event t h a t occurs i s t h e command nodule i n i t i a t e st h e deployment of t h e spacecraft LM veh i c l e pane l s which

are blown away pyrotechnically, The command module proceedsaway from t h e S-IVB, does a 180-degree maneuver, comes backi n , docks w i t h t h e lunar module, and t hen t h e t w o of themback away from t h e S-IVB.Next chart, please.(S l i de )T h i s is t h e n a c o n f i g u r a t i o n of t h e t w o spacecraf ti n t h e dock Configurat ion throughout t h e t r a n s l u n a r phase of

t h e mission.Next s l i d e , please,( S l i d e )Now, a f t e r t h e t w o spacecraft have suc ces s fu l l yaccompl ished the t ransposi t ion and docking and have separatedan acceptable d i s t a n c e away from t h e S-IVB, t h e S-IVB w i l lbe passivated and put i n t o a s l in gs ho t maneuver w h i c h i n e f-

f ec t causes it t o t r a v e r s e a t r a j ec t o ry as shown here , whereint h e g r a v i t y f i e l d of t h e moon is used t o force t h a t v e h i c l ei n t o a permanent solar o r b i t ,Next s l i d e , please.( S l i d e )The t i m e v a r i a t i o n t h a t w e a n t i c i p a t e as a f u n c t i o nof launch day and t h e t i m e i n t h e window when w e launch,t h i s being the beginnin on a p a r t i c u l a r day and t h i s t h e

end ( i n d i c a t i n g ) , v a r i e s from a minimum of 75.2 hours t o69.3 hours on t h e Past day of the window,T h a t d i f f e r e n c e is l a r g e l y a r e s u l t of the factt h a t t h e moonws o r b i t around t h e ea r th i s not c i r c u l a r but

e l l i p t i c a l , and therefore the, d i s t a n c e is a v a r i a b l e depend-i n g on t h e day of t e mon~ h hat we launch.


16/84

-6a-

4z0/

JI

./ ;


17/84

-6b-


18/84

uc


19/84

A T T A C I ! E N T TO

/mCL0

5-9640-H-205 -6d -

\I / V

rn0

0p:Q

P-iP

woc3(3


20/84

-6e-

3


21/84

7Next s l i d e , please,

One intere It thought w e would showtoday is a p l o t of t he t w o spacecraft a f t e rt h e t r a n s l u n a r i n j e c t i o n b ur n as it decreases, as w e moveaway from t h e i n a l l y w e reach t h e point wheret h e moon's gra h e n c e a c t u a l ly star ts t o speedt h e combination n p r i o r t o t h e t i m e t h a t w e dot h e l una r o r b i t

t h a t range of speed v a r i e s fromabout 25,000 m i l e s pe ur a t the time we l eave t h e ear tht o a loa of something t h e order of something less than500 m i l e s per hou and then f i n a l l y back up t o somethingl i k e 8,000 m i l e s p e r hour a t t i m e of i n j e c t i o n .

T h i s mission p r o f i l e i s planned, as w a s Apollo 8 ,w i t h fo ur midcourse c or re ct io ns going o u t , three coming back.And I mentioned previou lly t h a t w e w i l l use t h e two-stepi n j e c t i o n i n t o t h e f i n a l c i r c u l a r o r b i t around t h e moon.

ime co d u ra t i on i n l u n a r o r b i t isslighLly me x t slide, please,

I have a l r e a d y covered t h e two-stage l u n ar o r b i ti n s e r t i o n discuhssio Both of t h e burns involved are f ixeda t t i t u d e bu rn s, Bn t t h e veh ic l e is l i n e d up w i t h a par-t i c u l a r o r i e nt a t i on i n e r t i a l space, and then burned un t i lv e l o c i t y is a%tsrineci;i n a l midcourse maneuver as t h e spacecraftt h e veh ic l e i s rotated as shownhen t h e i n se r t i on bu rn is madene causes a retrograde o r s lowingdown o f t h e veh ic l e to place i t i n t h i s o r b i t .

a i n on the e away from t h e ear th t h e c i r c u l a r -k i n g maneuver i s made to find t h e place t o g e t to t h e 60n a u t i c a l m i l e o ~ ~ i ~ ~


22/84

-7a-

(1m c,N

I

0


23/84

-7b-

LuIn0LL0eRA

I I0


24/84

-7c-

0 x 170 WITH P L A N E CHANGE1(2)-60 x 60 IN P L A N E

F I X E D ATTIT E BURNS


25/84


26/84

8( S l i d e )Now, i n order to acquaint you a l l w i t h some of t h e

acronyms t h a t we u s e q u i t e broadly on t h e program, I havel i s t e d some of t h e key ones i n t h e next s l i d e . Let m e takej u s t a moment here to go through them b r i e f l y t o give youa chance to read them.I t h i n k most of you are familiar w i t h MSFN, t h eManned Spaceflight Network.LOS means w e have lost'communication w i t h t h e space-c r a f t because it h as gone behind t h e moon.AUS is when we acqui re i t again.DPS is descent propuls ion sys tem o f t h e lunar moduleAPS is t h e ascent propuls ion system of t h e l u n a rmodule.DO1 i s t h e descent o r b i t i n s e r t i o n t h a t t h e l u n a rmodule makes i n i t s move down towards t h e 50,000-foot a l t i t u d eCSI is one of t h e rendezvous maneuvers cal led con-c e n t r i c sequence i n i t i a t i o n , which Colonel McMullen w i l l dis-c u ss i n more d e t a i l , as w i l l he dirscuss CDH o r cons tan td i f f e r e n t i a l h e i g h t maneuvers.TPI is approaching t h e f i n a l phase of t h e rendezvoust h e so-called t e r m i n a l phase i n i t i a t i o n .PC here i s used as plane change, s i nc e there is a l-ways some small re s i du al p lane change required t o b r i n g t h et w o spacecraft back toge ther i n t h e same i n e r t i a l pla ne.Next s l i d e , please.NOW, t h i s char t emphasizes t w o poin t s . We have workvery hard on t h e F mission t o m a k e t h e t i m e l i n e from t h e timet h e spacecraft go i n t o t h e f i r s t l una r o r b i t u n t i l t h e y comeback ou t on t h e i r w2y home as close as w e c a n t o t h e l u n a rlanding G mission. And, as you w i l l see, t h e f i r s t 30-somehours of these two missions are planned t o be i d e n t i c a l .


27/84

>-W

-v)

Ev,LLz070

cn3L

I

844:I

5IW3CYWv)

W

3a0CLI


28/84

b

Ea0c

c-.wI-

Y [-

NI5 7-O-J*Iu-x

1"1"


29/84

. N

rt

W e # -


30/84

-8d-

nLa-c.

a


31/84

9I would also p o i n t o u t t h a t we have arranged t h i smission such t h a t t h e rendezvous for t h e t w o missions areas close t o i d e n t i c a l as w e can make them.The one unique fe a t ur e i n t h e F mission is t h a t w ehave a phasing burn e a r l i e r and special only to the F missionwhich ea r l i e r i n t h e l u n a r o r b i t t i m e l i n e se t s up condi t ionsso t h a t a rendezvous can be conducted here ra ther t h a n here( i n d i ca t i n g ) i n t h e t i m e l i n e u nde r t h e same cond i t i ons ofl i g h t i n g and other parameters r e l a t i v e t o t h a t o r b i t a l geo-metry exe rc i s e .I n t h e case of t h e G mission, of course , we havet h i s block of t i m e B e t o u t f o r t h e descen t , t h e l una r su r f acea c t i v i t i e s , and r e t u r n back t o l u na r o r b i t ,W have transposed t h a t w i t h t h i s block of t i m e onth e F mission ( ind ica t ing) and w i l l use t h i s t o provide addi -t iona l photography and landmark tracking of c e r t a i n selectedkey landmarks on t h e l una r su r f ace .One other poin t . I apologize for an error on t h i schart. W e should have s tar ted o u r t i m e bar here a t LOI-1instead of t h e l a s t midcourse maneuver, and then t h a t p l u st h e fac t t h a t w e l e f t o u t a l i t t l e block of t i m e here ( indi-

cating)-- I t t u r n s o u t t h a t t h e t i m e in o r b i t from LO1 u n t i lTEI is a c t u a l l y a l i t t l e over 61 hours. So there is an e r r o ri n t h a t t i m e scale.With those comments, I would l i k e t o ask Tom McMullt o lead you through t h e s teps i n t h e rendezvous maneuvers.McMULLEN: Thank you, George.Can we go t o t h e next s l i d e , please.( S l i d e )As I go through t h e d i scus s ion here, I would l i k et o emphasize t h e po in t t h a t Mr. Hage has already made -- t h egreat dea l of e f f o r t t h a t h a s gone i n t o making t h e maneuversa t l una r d i s t ance du r ing t h i s mission s imi l a r t o those w ew i l l a c t u a l l y be performing on lunar landing m i s s i o n next t i m e


32/84

10Let m e exp la in a l i t t l e b i t t h e s l i d e before w ea l so get into discussing maneuvers themselves,You can see w e have two p l o t s o f t h e spacecraft ,

t h i s one down here and t h i s one up here. The one o n t h e r i g h t -hand s i d e is what you would see i f you were s tand ing of f some-where i n space and looking a t t h e moon w i t h t h e t w o spacecraf tgoing around, So you can imagine yourself somewhere out i nspace, say on t h e ea r t h , w i t h good e y e s , and have a b i l i t y t osee t h i s amount of d e t a i l .The scale, of course , is n o t q u i t e t r u e , i n t h a t t h eo r b i t s are shown quite a b i t h i g h e r o r la rger w i t h respect t ot h e s i ze of t h e moon.W have t h e moon divided i n t t , d i f fe re nt colors here.The s o l i d shows when b o th t h e spacecraft and t h e l u n a r s u r f a c eare in darkness. The next t w o pie-shaped areas show when thespacecraft is i l lumina ted by t h e sun but t h e s u r f a c e still. isdark. And, of course , on t h e upper right-hand s i d e , b o t ht h e spacecraft and t h e l u n a r s u r f a c e are i l lumina ted .Over on t h e lower. l e f t here w e have a p l o t w hi chs h o w s t h e r e l a t i ve mo t ion of t h e t w o veh ic l e s t o each o t h e r ,and on t h i s one you can imagine t h a t you are s i t t i n g on top

of t h e command and s e r v i c e module and watching t h e LM maneuverabout you,Okay. So now I t h i n k w e are ready t o go ahead andd i s c u s s t h e f i r s t maneuver, and i t is t h e separa t ion maneuver,

I t i s q u i t e s imi la r t o t h e se pa ra ti on maneuver w e made ont h e Apollo 9 m is si on j u s t completed, I t consis t s of a s m a l lr a d i a l burn by t h e command and s er v ic e module usi ng t h e s e r v i c er e a c t i o n c o n t r o l system, T h i s is two-and-a-half f e e t p e rsecond, And it g ives t h e command and s er v ic e module a smallincrement of downward veloci ty .

T h i s does not change t h e per iod of t h e command andservice module, so t h e l u na r module and command and se r v i c emodule are s t i l l going around t h e moon and w i l l complete oneo r b i t in t h e same l eng th of t i m e , However, it does providea maximum of about 1.8 n a u t i c a l m i l e s between t h e t w o andabout a h a l f a m i l e i n h e i g h t .And here w e see t h a t al though t h e burn is made byt h e command and s e r v i c e u l e , it wou t h e command

and behind it,and service module as 1& h t h e lu na r going up


33/84

I

' 4:


34/84

And a f t e r % h i smal l burn, t h e t w o veh ic l e s w i l lseparate, and as t h e l un a r module d r i f t s up and behind t h ecommand and service d u l e , c e r t a i n checks w i l l be made t obe s u r e w e want t o proceed,And i f w e decide not t o proceed, w e j u s t w it ho utany further burns continue on around t h i s maneuver line hereu n t i l t h e t w o are back together, and a very small burn, andthey would again be back i n t h e same o r b i t .However, i f t h e systems look good, t h e rendezvousappears t o be working s a t i s f a c t o r i l y , a t t h i s p o i n t then w ew i l l perform our descen t o r b i t inse r t ion burn .Next s l i d e , please,(S l ide)The descen t o r b i t i n s e r t i o n burn is a maneuver t h a ti s performed by t h e lunar module descent; propulsion sys t em.It starts up w i t h t h e rocket engine t h r o t t l e d up to 10 p e rc e n t f o r about 15 seconds, and then t h e t h r o t t l e i p J advancedt o 40 p e r c e n t f o r t h e remainder of t h e burn, which is aboutanother 11 seconds.A t t h e end of t h i s burn, t h e two veh ic l e s w i l l bei n t h e o r b i t s as shown here w i t h t h e l u n a r module descendingdownward closer t o t h e l u n a r surface and t h e comrnand andservice moduie continuing on around t h i s f a i r l y c i r cu l a ro r b i t ,One of t h e other p o i n t s I should have mentionedis w e show on these c h a r t s t h e p o i n t a t which t h e MannedS p a c e f l i g h t N e t w o r k w i l l acquire and 10S8 s i g h t o f t h e l u n a rmodule as i t goes behind t h e moon.A l s o , on t h e r e l a t i ve mo t ion p l o t here now, w e seet h e sepa r a t ion bu rn is t h i s s m a l l dot ted l i n e r i g h t here t oa d i f f e r e n t scale t h a n we saw pr ev io us ly , And th en w e alsosee t h e descen t o r b i t -- t h e r e s u l t s of the descen t o r b i ti n s e r t i o n -- as t h e lu na r module now moves downl passesd i r e c t l y underneath t h e c and and s e r v i c e module by about20 n a u t i c a l m i l e s g d erencet and then proceeds o n downwhere it reaches 8command and service talle .aance of 52 ~ ~ u t ~ c ~ ~i l e s b e l o w t h e


35/84

-1la-

0

cyh e


36/84

Alar to the way i tg mission, butng radar checkout.

we havenp a c ~ c ~ ~ ~ tlight400 seconds ort e s t , And ehic le i n t h i se to t h e lunar

e r t i c a l , andfrom a l l foure i t s v e r t i c a l


37/84

*>;U4

-12a-


38/84

B

be th e ph moment ago,Ca

A l i t t l e bit phasing burnwe would have.In t h i s case,and w e get to

anding mission.sformed w i t h the

descent prspulbs e maneuver toincrease vePoei synth ion d i s tances p e c i f i c a l l y w i t f b c r e a s i n g the periodof t h e orbi-t so in f r ont of andbelow the CS nd and below theCSY. i

n system is againt h r o t t l e d It 26 seconds ,and then. t ixed throttlewhich is a e remainder ofthe B u m ,

194 nauticalthe commandmodule willcast off and

illt h i s


39/84

II


40/84

!A -13b-


41/84

14t o l i f t i n g off t h e l una r su r f ace , and we have a problemof s u b t r a c t i n g o u t ve loc i ty as opposed t o we w i l l beadding a t t h i s po in t on t h e lunar l and ing ,

W w i l l need to s u b t r a c t off some of t h e veloci tyt h a t w e added prev ious ly i n order t o have our apolune o rapocynthion h e i g h t of 45 nau t i ca l m i l e s . So t h i s is t h epo in t w e are t a lk ing about up here 45 n a u t i c a l m i l e s abovet h e l una r surface.A s a br ie f recap over here on t h e r e l a t i v e motionplot , you can see t h e phasing maneuver took place way up,and w e pass behind as w e pass through t h e . . . d i s t a n c eabove the CSM and drop behind and again b e l o w , so w e areat t h i s point here where again w e are ready t o s u b t r a c to u t some ve loc i ty and move ourse lves up to a po in t 15 naut i -c a l m i l e s below t h e command and se rv ic e module c i r c u l a r o r b i t .This burn w i l l be performed by t h e ascen t p ropuls ionsystem which is a n u n t h r o t t l e a b l e e ng in e, 213 foot per seconds u b t r a c t i o n of ve loc i ty .May we have t h e next s l i d e , please.( S l i d e )The next maneuver is t h e concen t r i c s equence in i t i -a t i o n , a n d , as pointed out e a r l i e r , i t occurs a t a h e i g h tabove t h e l u n a r s u r f a c e of 45 n a u t i c a l m i l e s , so w e arenow 15 m i l e s below t h e command and s e r v i c e module o r b i t .And t h i s is an add i t i on of v e l o c i t y so as t o ra i se t h eapocynthion from i t s 50,000 fee t o r i g i n a l d i s t a n ce up t oaga in 45 nau t i ca l m i l e s so w e are now i n c i r cu l a r o r b i tbelow t h e command and s e r v i c e module.This is done by t h e lunar module RCS, and i t is a

s m a l l burn, about 50 f ee t per second.Okay. The next burn t h a t w e w i l l discuss-- Iguess I should po in t ou t over here on t h i s r e l a t i v e motionp l o t t ha t now t h i s c i r c u l a r o r b i t will appear as a s t r a i g h tl i n e as w e mainta in our 1 5 n a u t i c a l m i l e d i s t a n c e belowt h e CSM.


42/84

0

U

/1II

-sihPc

I

\- 0

I \z0-0E

z \P I

I/


43/84

e requirementone plane t o ano%he g through t h epo in t a long t h e l i n e p l anes co inc ide .So i n order t o forcec o n s t a n t d i f f e r e n t P a l

IL change f r o m

s o m e value, t o forcend and service

Okay. W e c(Sl ide)

W e w i l l discuss t t d i f f e r e n t i a l h e i g h tburn. An d t h i s is ~ o ~ i ~ a ~ ~i x fee t per second andagain performed by t h e l una r le r e a c t i o n c o n t r o l system.And t h i s can provide any nge a gai n requi red t oensure t h a t t h e f i n a l re aneuvers are co-planer --t h a t is, t h e tw o vehic les are in t h e same plane -- and alsof o r any h e i g h t adjustment required,And again we are here on t h e r e l a t i vemotion plot w i t h an expandew e press on around t h e t r a j t o r y Course, t h e terminal phasei n i t i a t e p oin t , t h a t we are c o n ~ t a ~ ~e i g h t b e l o w t h e

o r b i t of t h e CSM,

nd YOU can see how as

el ide and as w eOur e l e v a t i o n a n g lefrom t h e l u n a r modu and s e r v i c e moduleis about 26 degrees,along t h a t l i n e af raise t h e h e i g h tof t h e lunar module nar s u r f s e e to 60m i l e s , which will let t h e o r b i t of t h e8 b u r n e s s e n t i a l l y

tens, any correc-e naidcoursec o r r e c t i o n poilits ZWgPeSSeS,f three brak ingmaneuvers almost d a t t h i s


44/84

-15a-


45/84

16p o i n t f o r t o t a l d e l t a V used during t h e braking process of30 t o 32 fee t per second, and again it w i l l be performedus ing t h e lunar module rea c t i on co n t ro l system.

So w e have t h e lunar module being t h e a c t i v e space-c ra f t dur ing t h e rendezvous.Of course , t h e purpose of t h e braking maneuver ist o c i r c u l a r i z e t h e lu na r module's o r b i t i n exac t ly t h e sameo r b i t as t h e command and se r vi c e module.And then a t t h i s po in t w e w i l l go ahead and dockt h e t w o veh ic l e s , t h i s t i m e I be l ieve us ing t h e command andse rv ic e module as t h e a c t i v e spacecraft.Okay. Then, a t t h a t po in t , w e w i l l go ahead andt r a n s f e r t h e crew back from t h e lu na r module i n t o t h e commandand service module.Can we go t o t h e next chart, please.(S l ide)And here we see t h e Lb! be ing j e t t i soned a f t e r t h ecrew has t r an s fe r re d back. And t h i s 90 6 is about 90 degrees

east long i tude on t h e l una r su r f ace.And then as t h e t w o veh ic l e s come around, t h e commaand s e r v i c e module w f l l make a small burn t o separate t h e t w oabout t w o fee t p er second, and it is about 45 degrees offfrom t h e lunar module.A s w e pass on around on t h e zero degrees l ong i tude ,which is, of course- The ear th is d i r e c t l y down t h i s d i s -tance . The ascent propuls ion sys tem w i l l again be lit t o

perform an APS burn t o deple t ion .T h i s is performed on t h e abort guidance system.

A l l t h e other maneuvers w e have seen have been performedon t h e primary av ia t i on guidance sy s t e m on t h e LM.On t h i s one, i n order t o get t h e check on t h eac tua l swi tch ing . e . W are adding approximately 3,800 f ee


46/84

/I

II\

i

wv,I . . - rn


47/84

T h a t ' s about all Emaneuverse Mr, Hage w i lof t h e missioAus up th ro heSubsequent t o comp t h e ascent burnand t h e LM ascen to r b i t s doing landmark s i g h ~ i n g ~ cribe what t h a t is .

Next s l i d e , please,(S l ide)One of t h e m o s t precli ave of loca t -i ng no t only i n l a t ~ t u d ~n va t ion spec i f i clandmarks such as a l i p (o small protuberanceon t h e s u r f a c e of t h e moo t landmark w i t h t h eop t i ca l t r a c k i n g s y s t e m a e and a t d ia -

Crete po in t s a long t h e ~r grees or sorecord i n t o t h e computer a t t h e o p t i c a ls y s t e m had t o be s e t a n ~ ~ ~i g h ti n t h e cross-hairs of t h e

With t h a tf l i g h t Network t rack h a t t h e o r b i t oft h e command and serv s p e c i f i c passover a landmark, i t is 9 y convent ionalsurveying t r i g o n o ~ e ~ ~ ~oand t h e l a t i t u d e and Ion i c landmark.A s I mentione several o r b i t sconducting those kind o ted by addi -t i o n a l ~ h ~ t o g r a p ~ ~ *


48/84

-17a-


49/84

18Now, t h e t r a n s e a r t h i n j e c t i o n is very s i m i l a r t ot h a t t h a t w e had o n Apollo 8 , Our t i m e i n o r b i t is aboutdouble what w e had on Apollo 8 . W are t a r g e t i n g f o r t h e

same genera l l and ing area 165 degrees west longi tude, whichis an area w e s t and south of H a w a i i .W are not a t tempt ing t o c o n t r o l t h e l a t i t u d e aswe d i d not on previous f l i g h t s ,Our normal entry ang l e is as shown, and I w i l l d i s -c u s s t h a t i n a l i t t l e more d e t a i l ,W w i l l use whatever r e s idua l p ropu l s ive capacityw e have i n t h e s er v ic e module t o reduce t h e r e t u r n t i m efrom t h e moon.And a l l of t h e t r a nse a r t h i n j ec t ion burns and t h emidcourse burns w i l l be done w i t h a f ix e d a t t i t u d e of t h ecommand s e r v i c e module,Next s l i d e , please.(S l ide)Now, t h i s is t h e conf igu ra t ion which you are a l lfamil ia r w i t h of t h e vehicle coming home from t h e moon, antenndeployed as shown.I thought I would comment j u s t b r i e f l y here on adiagram t h a t I t h i n k gives you a p r e t t y good represen ta t ionof what happens i f you don' t have c a p a b i l i t y of making m i d -cour se co r r ec t ions ,Each and any one of these propulsion burns windup w i t h some residual errors t o t h a t t h a t w a s s p e c i f i c a l l yplanned. If one permits those errors t o propagate withoutc o r r e c t i o n , t h e n w e f i n d t h a t w e have a diver ging cone ont h a t t r a j ec t o ry , So w e s e t c e r t a i n m is si on r u l e s t o permi tt h a t t o grow wi th in acceptable l i m i t s , and t h e n w e m a k e a m i d -course cor rec t io n and br in g t h e v e h i c l e back on t r a j e c to ryand t rack i t and watch f o r evidence of errors i n t h a t m i d -course correction, u n t i l f i n a l l y w e f i n d t h e vehic le on anacceptable p a t h l ead ing t o t h e f i n a l separat ion of t h ecommand module and e n t e r i n i n t o t h e narrow entry cor r idor ,


50/84

-18a-

Z0c)

0- I 3

PL wI Q3u) c

n0z0v

Lu4A

Ly

nlaac-wLyc(34

L u-Im44>44->aZILu3

00wV


51/84

-18b-

f-..t),.. ._ Ap _ .

L - .


52/84

' .

P 3L-.2 am


53/84

19You may remember on ApolPo 8 t h e t ransea r th i n j e c t i o nburn w a s so precise t h a t w e could have, i f w e had elected t o ,e s s e n t i a l l y l e t t h e veh ic l e come home without any f u r t h e rmaneuvers, W e d i d decide t o make a small t r i m burn about h a l f -way home. Next chart , please,( S l i d e )Thi s chart gives you some f e e l fo r t h e v a r i a t i o ni n to ta l mission time i n h ou rs , where 192 here representse igh t ca l enda r days. And, ag you can see, it is a l i t t l eover e i g h t ca lendar days i f w e launch r i g h t a t t h e beginning

of t h e f i r s t launch window on t h e 1 8 t h .The t i m e of t h e mission can vary from t h i s l i m i tof 187 hours up t o t h i s l i m i t which is something i n ex cessof 197 hours , o r , i n other words, a p o s s i b l e v a r i a t i o n of asmuch as t e n hours depending on which day and which p a r t oft h e launch window w e g e t on.Next s l i d e , please.( S l i d e )The e n t r y i s t y p i c a l of t h a t t h a t we demonstratedon Apollo 8 , We have c a p a b i l i t y f o r a very la rge r e e n t r ymaneuver footprint , 1,200 t o 2,500 n a u t i c a l m i l e s . W e w i l lnominally target f o r 1,350.T h i s t ends t o enhance our a b i l i t y t o make a goodr e e n t r y i n t h e event t h a t w e have t o use one of t h e backupco nt ro l modes or guidance mode.We w i l l allow fo r weather avoidance i n t h e recoveryarea by ta rge t ing f o r a change i n t h e veh ic l e t r a j ec to ryabout one day p r i o r t o r e e n t r y if t h e weather i n t h e recoveryarea looks l i k e it is beyond acceptable l i m i t s .Next s l i d e , please,( S l i d e )

bout t h e r e e n t r y corridor. I t ' sh t p a t h angle t o t h elocal h o r i z o n t a l of % he ~ t m ~ s ~ h @ r ~t t h e p o i n t t h a t you


54/84

-19a-

3

L..a Ycy


55/84

I I I 1 I


56/84

-1gc-

W

I

0u)c3

0(Y7I cc

>- Iu-l--1- (3m Z.cc 4e CY

->-CY4V

W I-Z(3Z4tY Z). -W-J

z0W ZCYI-

0 0

V0

0

z4 < z * WCY fY I-I - 0 v)2.v)z oW WZCY0I 0u) c o

t-fY

5

0

ZI-t-

cz00ZnZQ0Z4IV

-L1

-AW

0c


57/84

-1gd-

a

mNhN

Mcnu3N


58/84

command module.to experience

acceleratfo 0% the machineryt h a t have to dowith the the Id. Th i s l ongstt d i s s i p a t e i n8 limit to t h eis 11tA11e one here i sto ta l heat, and % heat you can

~ r ~ j ~ ~ t o re in t h i s r e g i o nt h i s po i n t tha t

get drogue and


59/84

-20a-

thI 4u, w

4-

c 70P- I-x00--t

I I0

(Y *r) cv

UI-wn0w

I-30YVQ:-.ImQZ4acnI-X

I

-w-

09 a0.-4111n

3 k -+ L LI-A

0cy'rtI Ic

..P

cz0aIV3

3

0t-

3

00N

00w

009

0000

000c

00cyc

00


60/84

-20b-

0-Q 0 0* m

I3'v = mV,

Iv

.a. Ia- !

0 0cv *

i;

00' -0cvc

0d

0a - 0c n3c-

(3Z0A


61/84

21Next s l i d e , please.( S l i d e )As I mentioned ea r l i e r , t h e nominal splashdown

longi tude is 165 degrees w e s t l o n g i t u d e , j u s t a l i t t l e b i tw e s t of H a w a i i and south. Fur ther so uth on t h e 1 8 t h . Closert o H a w a i i on t h e 20.t;h.And then to make s u r e w e avoided the i s l a n d grouph e r e around H a w a i i , w e moved over to 175 degrees w e s t longi -tude on t h e 23rd, 24421, and 25th .Next s l i d e , please .(S l ide)I would l i k e to talk j u s t b r i e f l y about some oft h e launch abort c a p a b i l i t y t h a t w e have i n t h e sys tem.I t has been i n t h e mission r u l e s from t h e beginning of t h eprogram, We b a s i c a l l y have four modes of abort dur i ng t h elaunch phase , l i s t e d X through IV as shown here,The i r basic differences are:Mode I abort uses launch escape tower.Mode 11 abort m e r e l y allows t h e command servicemodule t a use a l i t t l e RCS t h r u s t t o get away from t h e launchv e h i c l e and t h en it goes on and coasts, separates , and re-e n t e r s a t a s u b o r b i t a l v e l o c i t y u s i ng t h e normal chuterecovery.Mode XI1 abort is t h e h i g h e r ve l oc i t y one whichr e q u i r e s that we burn t h e SPS sys tem i n a retrograde wayto slow t h e vehicle down for r een t ry .F i n a l l y , Mode IV is an abort mode where w e u s et h e c a p a b i l i t y of t h e S-IVB as shown here s t a g i n g offt h e S-I1 e a r l i e r i n t h e even t w e have a problem t o car ry

t h e v e h i c l e on up i n t o o r b i t .The c a p a b i l i t y s ta r t s a t about a l i t t l e sh o r t ofsix mi nu t es i n t o t h e launch phase.


62/84

- ?'.a 'i. . . .. -. . .

..._.-I

-21a-


63/84

-21b-

N

0 .0

c* * ,

2..00'

Dwm4Awa

n


64/84

22We also have capab i l i ty i f w e have problems a tt h i s per iod of t i m e t o use t h e se r v i c e p ropul s ion systemi n an ac ce le ra t i ng way t o carry t h e vehic le on up i n t oo r b i t .The conclus ion t h a t w e have come t o is t h a t whenone gets u p i n t o these higher v e l o c i t y port ions of t h elaunch phase, t h e sa fes t t y p e of abort is one in to o r b i t ,where you can take some t i m e t o s o r t o u t t h e problem andthen perform t h e n o r m a l reen t ry .Next s l i d e , please,(S l ide)T h i s mission, l i k e a l l previous miss ions , has i n -volved a number of a l t e r n a t e m is si on classes t h a t we areprepared t o f l y i n t h e event of d i f f i c u l t y . There are f o u rgener ic ones o n t h i s mission.Like t h e 9 mission, w e could be l i m i t e d t o a l o wear th o r b i t mission,We might f i n d o u r s e l v es w i t h a t r a n s l u n a r i n j e c t i o nburn on t h e part of t h e S-IVB t h a t e i t h e r l e aves us i n a

semi-synchronous earth o r b i t , w h i c h is very high apogee o r b i to r one t h a t is capable af taking circumlunar when w e uset h e sur fac e p ropuls ion eng ine t o put t h e l i t t l e b i t of e x t r aenergy required t o g e t u s o u t to t h e moon.If t h a t kind of an anomaly occurrbd, we may n o t bei n p o si t io n t o go i n t o l u na r o r b i t ,Obviously, t h e u l t i m a t e s i t u a t i o n is l una r o r b i topt ion.The ana ly s i s t e chn iques t h a t are employed i n de-veloping t h e r u l e s by which t h e f l i g h t direc tors select whichop t ion t o go i n t o in t h e event of t r o u b l e are shown on thenext s l i d e , and t h i s s l i d e is a r e p r e s e n t a t i v e example ofa log ic diagram where w e j u s t took t h i s one case where w ecompleted t h e t r a ns l una r in j ec t i on burn and t h e next even tis t h e LNI ex t rac t ion , and obvious ly t h e two options you havethere are e i t h e r , "Yes, w e are able t o , " or "No."


65/84

-22a-

Lnwm40

I-mPL0sc-

-

2b-smlx0lxs3


66/84

-22b-

ln

CIL0


67/84

it

23If t h e answer is ' ~ y e s g fnd w e are able t o completet h e lun ar module ex t r ac t i on , w e follow t h i s path .If "no," w e go down another p a th which h a s as imilar s t r u c t u r e t o i t ,Each one of these p a t h s leads t o a se t of missionr u l e s t h a t lead t o a n a l t e r n a t e mission,For example, i f at t h e time of TLI w e found t h a tt h e burn w a s short and would r e s u l t i n a maximum a l t i t u d earound t h e earth of around 13,000 m i l e s , w e would modifyt h a t o r b i t and come down t o a CSM/'LM l o w ear th o r b i t a l rendez-vous mission very similar t o what w e d i d on Apollo 9.If t h e burn w a s greater than t h a t requ i red t o get;t o 13,000 m i l e s apogee, we would go on in to t h i s dec i s ionblock ( ind ica t ing) which looks a t t h e c a p a b i l i t y of t h a tTLI burn and could le av e u s e i t h e r w i t h t h e op t ion t o goi n t o a lun ar miss ion o r go down i n t o a mission which is avery h i g h e a r t h o r b i t a l mission t h a t would not permi t u s t omodify it back down t o low o r b i t a l mission because of t h el i m i t e d d e l t a V p r o p e l l a n t s aboard t h e se rv ic e module,Now, there is a whole f a m i l y of these d e c i s i o nblocks t h a t are use d ' i n develop ing t h e pyramid of a l t e r n a t emissions t h a t f a l l below these three genet ic categories ,Next s l i d e , please,( S l i d e )I would l i k e t o t a l k j u s t f o r a moment here aboutt h e Apollo 10 TV o p e r a t i o n a l p l a ns ,through and read t h i s char t , I don't propose t o go

J u s t before coming down t o t h e b r i e f i n g , I wasadv i sed tha t t h e l a t e s t planning ca l l s f o r a t o t a l of 11d i f f e r e n t crew ope ra t ions i nvo lv ing TV. They are scat teredthroughout t h e mission, and most of them are about 15 minutesi n d u ra t io n ,As you w i l l note here, it is o u r i n t e n t t o f l y anexperiment involving color TV i f w e can develop i t and g e t

it prepared t o fly in t i m e to suppor t t h i s mis s ion ,


68/84

,

TII-e4WYCE0EX

S E n- J 7

W

I

-fxwIXW- -

20zWn7WCL

a

08


69/84

0Jaa

Z Eo o-..I= 5I '

n

Cl137a

I-owav,7-3iJ

7war:%II-oas:2

111wc30c-0

av)W-c

I-3XWv)

sI-o43z0

tIa.


70/84

fabout a 59-50t h e p i c t u res and white.T h i s g i v e s you a s ~ o r t on t h e periodsd u r i n g t h e mission when we would g var i ous k i nds o ft e l e v i s i o n c ov er ag e ea c t u a l l y now p ~ ~ ~ ~ e ~ ,per iods ofNext s l i d e , please.(SlideI n a d d i t i o n t o t W Q ~ ~ ~e c a r r y i n gt h e standard complement of s t i l l cameras and t h eMauer 16 mm, movie cameras, e lunar and commandmodulesThese cameras w i l l be used i n consonance w i t h t h ephotographic f l i g h t p l an t h a t has been developed w i t h t h ecrew t o cover these c r i t i c a l p

(S l i de )

a g e o m e t r ye ~ ~ a v ~ l l i n ghe period oft i m e t h a t t e v i c i n i t y of t h e

ents on the missions e s s i o n t o


71/84

25I t h i n k it ha s been shown before p o s s i b l y p r i o rt o t h e Apol lo 8 missio i f there are enough of youwho are i n t e r e s t e d i n see ing it, I t h i n k you might f i n d i tvery good i n c l a r i f y i ng some of these c o n s t r a i n t s t h a t wehave t o l i v e w i t h i n f l y i n g these missions t h a t are a r e s u l tof na ture ,0'DQIWEL.L: e w i l l take a f e w ques t ions from here,then go t o Houston, a then r e t u r n here,QUESTION: On t h e launch phase, have, there beenany unmanned launches f or i s t h i s the f i r s t t i m et h a t pad w i l l be uHAGE : t had any previous launchesoff of it. T f i r s t launch off of t h a t pad,

he Apollo facand t h e p h i l overy obvious one, i n t h a t w e foundis t h e wrong number inrogrant had t h e misfor tune t o be facedpad, Then there wouldn e pad back up t o an

So we have 8 planned to have t w o pads t o sup-por t the ~~~~~ ng mission attempt.I

0' DQNNSELL: er here.QUESTION: H understand there is a reason why t h i slu na r module 4 could not land on the moon even if it was

desired to do so, Would you e x p l a i n t h a t reason, Mr, Hage?The ~u~~~ module being flown on t h i s

@ ~ u ~ ~f dec id ing t h a t we were going tosubsequent f o r t h e landing at tempt andad planned t o fly an F mission fo r some -

f d e f i c i e n c ie s i n i t s equipment

~ ~ n ~ i ~ ~adar.on t h a t a l i t t l e b i t . T h en ~ u ~ ~ n t e dn such a way thatoperat ion f l y i n g through t h a t


72/84

l one1 McMuItenradar of aboutwould be usedse on the sur-

to something

n augmented t o provideg radar before w et h e G mission.

8 one t h a t we have controlalf t h e p r o p e l l a n t s in the02 t h e ascen t stage dur ingorder to m o r e nea r ly

t h e rendezvous phase of t h e mission.1 am sure you can u ~ d ~ ~ ~ t ~ n ~h a t t h e l una r module

t stage is about h a l f prope l l an t and about h a l f equip-ment, And when you take o f from t h e moon t h e vehicle weighs~ ~ ~ r o ~ ~ ~ a ~ ~ l y0,000 pounds, and by t h e t i m e you reach orbitand are ready to dock, it's altmose down to 5,000 pounds.is is 8 very large change i n weight and i n e r t i a , and weve off-loaded this vehicle to nore nea r ly match t h e dynamiccond i t i ons of c o n t r o l that t h e crew w i l l be faced with duringthe actual rendezvous and d ~ ~ ~ I ~ ~ ,

STHON: S e v e r a l questions. What will t h e l i g h t -i n g of t h e moon be at the time of t launch? Will i t bea ~ a ~ ~ - r n ~ ~ ~ ?rescent moon?

that h e r e , Thethat chart of thei t y in July Is an the 16th, and t h a t is forat t h a t target will beand t h a t target is

erlymost limb. If youut 30 degrees around.

N: e 29 up, P t i n k we could seeit, Slide 24 up, please ,

escent off of a new moor l ,and at will be


73/84

HAGE: Here's t h e d i r e c t i o n t o t h e earth. And,as you can see, you w i l l see t h i s l i t t l e p i e as lit byth e sun, and t h a t i n effect w i l l g i v e you a new crescent,about a half-formed new c r e s c e n t , halfway between a newmoon and a half-moon,

QUESTION: And t h e o ther par t of my ques t ion w a s :I didn ' t unders tand t h e reason behind t h e h i g h apolune of194 n a u t i c a l m i l e s . Because you don't have t o go t h a t h i g hi n t h e actual planned mission.M c M U L L E N : T ha t ' s correct. But, you see, w e ares t a r t i n g off- let 's see. The period of a body revolvingabout another one is a func t ion of a l o t of t h ings , one of

which is t h e size of t h e o r b i t , t h e semi-major axis. Sowhen w e s t a r t our descen t o r b i t i n se r t i on , obv ious ly we arecu t t i ng down t h e s ize of t h e semi-major ax i s . As a r e s u l t ,w e are moving about the central body -- t h a t i s , about t h emoon -- fas te r than w e were o r i g i n a l l y , And t h e l una r modulewinds up i n f r o n t of t h e command and s e r v i c e module.Now, t h i s was no t t h e condi t ion w e would have f o rrendezvous o r f o r i n i t i a t i n g rendezvous on t h e lunar l and ingmission, I n fac t , we'd s t a r t off w i t h t h e lunar module

behind.So, obviously, somehow w e have t o g e t t h e l una rmodule back behind t h e command and s e r v i c e module. Andus ing t h e same rule t h a t we j u s t d i e c u s s e d , w e i n s e r t i ti n t o a rea l large o r b i t so t h e period of i t s r o t a t i o n a bo utt h e moon is very la rge , and, hence, it f a l l s behind thecommand and service module. I t winds up r i g h t a t t h e sameplace t h a t w e s ta r ted t h e maneuver, but it J u s t is somewhatd i f f e r e n t r e l a t i v e t o t h e command and service module.QUESTION: I have trouble remembering t h e meaningo r t h e purpose of t h e CSI and CDH maneuvers, and one reasonf do is I don't understand t h e meaning of those words"concen t r ic sequence in i t i a t ion" w i t h r e f e r ence t o t h eactual maneuver performed, And I was wondering i f you couldtake a couple of minutes t o exp la in t h e r e l a t i o n of t h e wordst o t h e maneuver.McMULLGN: Okay . I ' l l try. Could we haveChart 36 up, please?( S l i d e )


74/84

28The concen t r ic sequence in i t i a t i on - I guess Ir e a l l y c a n ' t t u r n t h e teras around, bu t t h e purpose ofb o t h t h e concen t r i c s equence in i t i a t i o n bu rn and t h e con-s t a n t d i f f e r e n t i a l h e i g h t burn is ts get u s i n t o a c i r c u l a ro r b i t a t a cons t an t h e i g h t below t h e command and se r v i c emodule o r b i t,So f guess a s imple way to say it is to m a k e s u r ew e are i n t h e same plane, t h a t w e are i n a c i r c u l a r o r b i tbehind and below t h e command and s e r v i c e module. The f a c tt h a t w e are below means t h a t we are going around f a s t e r ,and hence we w i l l be ca t ch ing up, so we w a n t t o s t a r t offfrom a po s i t i on beh ind.WAGE: May I h e l p a l i t t l e on t h a t ? One way t ot h i n k about t h a t is t h a t t h e maneuver a t t h i s poin t whichis labeled "Concent r ic sequence in i t i a t ion" does i n fac t ,i f i t is a perfect maneuver, put t h i s v eh ic le i n an o r b i tt h a t is c i r c u l a r and c o n c e nt r i c wi t h i n t h e CSM o r b i t -- i f

it is p e r f e c t .QUESTION: You are making one o r b i t concen t r i ct o t h e o ther o r b i t ?HAW:. Right .M cMUUN : Okay. I guess t o carry i t o n e f u r t h e r ,t h e c on st an t d i f f e r e n t i a l h e i g h t is t o ensure you maintainj u s t t h a t cons tan t difference i n h e i g h t above t h e s u r f a c eof t h e cent ra l body,QUESTION: I have a couple of que sti ons, one onth e per icyn thion, Can you giv e us i n m i l e s uprange of t h ea c t u a l l a nd i ng s i t e t h e poin t on t h e moon where t h e space-c r a f t w i l l be closest and why it w a s ad jus ted t h a t way?

In other words, what MASCON problems you are t r y i n g t o f i n d ,photography of more landing s i t e s t h a n j u s t o n e , t h a t k i n dof th ing.McMULLEN: I can answer t h e second one qu i t e clearlThe d i s t a n c e o r t h e po in t a t which w e a r r i v e a t per icyn th ionis determined by t h e geometry of t h e lunar landing miss ion.T h i s is a f a l l o u t from t r y i n g t o make t h i s mission i d e n t i c a lt o ' t h e lunar l and ing m i s s i o n , and i d e a l l y in t h e lunar l and inmission w e would a t t h e p o i n t of p e r i c y n t h i o n i n i t i a t e apower d e s c e n t )


75/84

29Tha t is t o s a y , w e would l i g h t t h e descent stageand continue t o burn as we s l o w t h e vehicle down andc o n t r o l i t s de sc en t down t o a landing a t t h e landing s i t e .Now, t h e d i s t a n c e ahead of t h e landing s i t e It h i n k is around 237 m i l e s , something l i k e t h a t .QUESTION: The second ques t ion is : You burn yourascen t p ropuls ion sys t em engine t o g e t r i d of t h e ascen tstage t o t e s t t h e abort guidance system, A t JPL t h e y madea proposal for a t ransponder in l u n a r o r b i t f o r about amonth f o r Apollo Applicat ions t o tmck it continuously t or e s o l v e this MASCON problem. Was there any considera t ionever g iven t o using t h e ascent propuls ion or t h e ascents t age -- t h a t is, l eav ing it i n l un ar o r b i t a f t e r you havedone some pro and con maneuvers, r e t ro and posigrade ands t u f f l i k e t h a t ?HAGE: I can9% s p e c i f i c a l l y answer whether o r n o tit was considered, I can comment on t h e fac t t h a t t h eb a t t e r y capaci ty of t h e ascen t s tage is l i m i t e d , and onApollo 9, as I recal l , a f t e r w e had separated t h e ascen ts tage and put it i n an unmanned mode and made a burn ont h e pr imary guidance sys tem, w e w e r e ab le t o get t e l e m e t r y

for something l i k e nine hours, and then t h e b a t t e r y w e n tdead ,So i n order to do what you suggested here I t h i n ki t would have req uir ed modi fic at i on of t h e spacecraf t .QUESTION: I understood you t o s a y t h a t t he rew i l l be 11 TI! op t ions , Could you g iv e u s t h e TV t i m e lineaga in , t h e 11 poin t s?HA=: I 'd be glad t o do t h a t . I wonder i f I

mi g h t l e ave i t here w i t h B i l l and you a l l can take i t , I tis a t e n t a t i v e fist, I mean t h e t i m e s are t e n t a t i v e .The crew w i l l exercise some opt ion on p r e c i s e l yvhen these windows open up, But there are 11 l i s t e d here.QUESTION: The t i m e w i l l be i n GET?


76/84

i the t r a n s c r i p t .atdon i n having t h e50,000 feet?

in g to d o on t h elunar landing decide on tha t ont h e lunar Ianave been made

l e for th e

th e moon. The e energy you musttake out of th e to slow t h e v e h i c l e

8 good compromisefor min i eight above t h es ur fac e to 2bGC rol ~ ~ ~ e ~ ~ ~ i n ~s of engineer ing

w e have i nthe t i m e you


77/84

sys e m.QUESTION : t h e eomnland modulew i l l be t h e active vehic le ng d o c k ~ ~ g ~s this the resultof t h e d i f f i c u l t y t h e l u n a r e r bad with beingthe active part in the do ?BAG%:: I wouH t~~~he dec i s ion t o usemodule f o r a di rec t r e s u l tl ea rned t h a t th the commandmodule, and we learned it on Apollo 9, although I would fur-t h e r have t o say t h a t there is a s t r o n g s u sp i c io n i n t h e

minds of t h e crews on t h e b a s i s of t h e i r s imula t ion workt h a t t h a t w i l l probably t u r n o u t to be t h e preferred mo d eeven before 9 was flown.QUESTION: For how long will you be a t 50,000 feet?T h ere i s a dot t ed l i n e o n t h e diagram. Cauld you w i t h yourp o i n t e r j u s t c on ti nu e t h a t and show where it goes from there,for how long it would be there?McMULLJEN: Could w e put slide 31 back up, please?(S l ide)If you look a t t h e s l i d e , you can no t i ce t h a t t h erad io l i n e s t h a t pass f r o m t h e s u r f a c e of the moon up t o thespacecraft are time-tagged. Pn other W CW ~ S , they start off

here a t t h e l e f t a t 600 seconds before reaching per icynthionand pass on down t o zero a t 100 hours and 51 minutes grounde lapsed t i m e , ascend up int e very large o r b i t , w e w i l lcome back down again t o ro 50,000 feet,HAGIS: I t h i n k t h i s diagram kind of exemplif ieswhat Tom may have mentioned earlier . This shows the moonas being round, and it is -- st, This orbit is e l l i p t i c a l .So t h e vehicle never is a taat ~ ~ t i ~ ~ ~t s t a r t s

g m s on up,i ghe r than 5 0 , O O dawn to $ 0 , ~ 0 0 ~nd then


78/84

6\

32QUESTION: A t t h i s po in t , on t h a t e lmaneuver, i f you have a spacecraft s t a r t i n g ofp o i n t on t h e s u r f a c e of t h e moon i n motion and i f YOU were

s i t t i n g o n t h e moon and couldn't . . , ( Inaudib le ) , , ,T h ere w e r e a number of op t ions , l i k e wai t ing f o r t h e commandmodule t o go around again, and a number of o t h e r t h i n g s ,I have had it suggested t o m e t h a t i f t h e t imingof t h i s burn, o r t h e i n t e n s i t y of it, is off by any appre-ciable amount t h a t t h e business of g e t t i n g t h e lu na r moduleand t h e command module back together again would be enormous-l y complicated. Would you comment on t h a t ?McMULLEN: Well, I: t h i n k we'd make a real-timeadjustment t o t h e phasing burn, A phasing burn is des ignedt o do j u s t exactly t h a t -- t o account fo r t h e d i f f e r e n c e i n

t i m e of t h e two s p a c e c r a f t pass ing s o m e po in t , So t h a t ifw e do have a problem g e t t i n g t h e burn o f f , it w i l l j u s t bea matter of changing t h e m o u n t of velocity change and hencet h e s ize of t h e o r b i t t h a t w e use f o r phasing, and t h a ta d j u s t s t h e t i m e automat ical ly .

QUESTION: Could you give me t h e t o t a l number ofo r b i t s t h e CSM w i l l make around t h e moon, t h e number ofo r b i t s it w i l l m a k e w i t h t h e LM detached and t h e t i m e fromTLI to LOI?HAGE: Y e s . As a r u l e of thumb, it is one o r b i tevery t w o hours. Tha t is a f a i r l y a c c u r a t e r u l e of thumb.I t w i l l be i n o r b i t 61-1/2 hours, and roughly 30 o r b i t s .Letts see. The second p a r t of your quest ion w a s --QUESTION: How many of those o r b i t s w i l l be w i t h

t h e LM detached?HAGE: With t h e LM detached'?QUESTION: Y e s .HAGE: Well, t h e LM is detached for a l i t t l e overe i g h t hours , so t h a t would be f o u r o r b i t s ,

I QUESTION: Another par t w a s t h e l eng th 01 t i m ef r o m TLI t o L O I .


79/84

33HA=: TLI to occurs at t w o hours and34 minutes from launch, CCUFS a t f i v e d ay s, 18 hours

and 26 minutes from launch,QUESTION: What aboutQUESTION: Could you repeat those f i g u r e s ?EA=: Translunar i n j e c t i o n , t w o hours and 34 minutesfrom launch, Lunar o r b i t i n s e r t i o n , t h e f i r s t o r b i t , t h e el-

l i p t i c a l orb i t , three days , fo ur hours , and 49 minutes, Andtransearth i n j e c t i o n , five days, 18 hours and 26 minutes,QUESTION: Once the l un ar module is detached andin its e l l i p t i c a l orb i t , if t h e ascen t eng ine fails is thereany way t h a t t h e command module can dock w i t h t h e lunar module?HAGE: Yes. L e t m e J u s t comment on t h e missionphilosophy, I t is i d e n t i c a l t o t b e philosophy we had on

A p o l l o 9. There is no s i t u a t i o n d ur in g t h e separated rendez-vous wherein there i s n ' t a backup propulsion m o d e a v a i l a b l ei n t h e event t h a t t h e primary m o d e f a i l s , such as us ing t h eRCS ins tead of t h e ascen t propuls ion, and on every maneuvert h e command module w i l l be t a r g e t i n g for a m i r r o r imagemaneuver, and in t h e event t h e LP$ i g n i t i o n does not takeplace, t h e command and service module w i l l i n e f f e c t makea mirror image maneuver t h a t would bring t h e t w o of t h e m backtogether again.

So no s ing le p ropu l s ion sys tem f a i l u r e would presenta c r e w hazard, s i n c e t h e r e is always an a l t e rna te o p t i o n wayof g e t t i n g t h e two vehic les together.QUESTION: Could we have t h a t GET char t up whilew e are t a lk ing? .HA=: Sure, C h a r t 12, please,( S l i d e )O'DONNELL: These charts will all be included in

t h e t r a n s c r i p t , i n c i ~ ~ ~ ~ a ~ ~ y ~Let's s w i t c hen w e come back, we

w i l l g e t some questio pb


80/84

34Does Houston have some quest ions?QUESTION: A s i m p l e quest ion. W e d i d n o t havet h e b e n e f i t of t h e s l i d e s t h a t you had i n Washington. W i l l

you give us throughout t h e e n t i r e m i s s i o n t h e GET t i m e f o rmajor op er a ti ons ? Would you give u s t h e spec i f i c launchdays and t h e spec i f ic timea of t h e windows for each day?Would you give us t h e GET t i m e s f o r t h e Ty?O'DONNELL: Those a l l w i l l be inc luded i n t h e t r ans -

c r ip t s t h a t w e w i l l get o u t tomorrow. W w i l l g e t them downt o Houston j u s t as soon as w e can.

Do you have any more ques t ions?QUESTION: However, t h a t doesn ' t h e l p i f w e arew r i t i n g a s t o r y t o n ig h t .HAGE: B i l l , can I suggest t h a t these might bes e n t by telephone d i r e c t l y a f t e r t h e b r i e f i n g ?O'WNNELL: A l l r i g h t . W e w i l l send them downby FAX machine. You should be g e t t i n g them i n another hour ,Okay. Back here now.QUESTION: I ' m i n t e r e s t e d i n t h e e a r l i e s t p o s s i b l elaunch. As I r eca l l , M r . Hage gave us 11:49 p.m., E.S.T.,making t h i s t h e ear l i e s t possible launch, and then l a t e rhe referred t o a d a y l i g h t launch and recovery. W i l l you c l e at h i s up fo r m e , please?HAGE: I ' l l t r y , 11:49 a . m . Eastern Standard Timeon t h e 1 8 t h , which r e s u l t s i n a d a y l i g h t launch and a day-l i g h t recovery .QUESTION: I s n ' t there some confusion f i r s t of a l l ,George? You keep say in g 11:49 Ea st er n Standar d, and t h ecountry is on d a y l i g h t .don ' t you? You mean 12:49,Eastern D a y l i g h t ,

HAGE: You've got m e on t h a t one, Jules. I t h i n kt h i s is s tandard t i m e . I t h i n k t h i s is computed i n s tan dar dt i m e , It has not been corrected f o r d a y l i g h t y e t .

QUESTION: Okay. Is there any chance a t a l l of ,t h e TV camera, black and w h i t e o r color, be ing operated from


81/84

35t h e LM dur i ng any of those l o w passes?

HAGE: No, t h e provis ions f o r t h e TV s y s t e mdon't ex i s t i n t h e lunar module, The a c t i v i t i e s t h a t t h ecrew w i l l be involved i n dur ing t h a t p h a s e of t h e missionare so demanding t h a t w e j u s t d i d n ' t make provis ion for it.

QUESTION: There is no way of s imply bracke t ingt h e camera on w h i l e t h e y are d o i n g t h e i r landmark s i g h t i n gand --HAGE: T h e r e are no e lec t r i ca l connections f o r t h ecamera i n LM-4.QUESTION: Could someone summarize t h e number ofburns t h a t w i l l be mads while you are i n l u n a r o r b i t andhow many of these w i l l take place o u t of s i g h t of t h e e a r t h ?HAGE: Both of t h e l u n a r o r b i t i n s e r t i o n burns,f i r s t t h e e l l i p t i c a l and then t h e c i r c u l a r o r b i t , are behindt h e moon, C o l o n e l McMullen is going through t h e ones involvedi n l un ar o r b i t .McMULLEN: T h e r e w i l l be a t o t a l of f i v e LM burnst h a t are out of s i g h t , of Manned Space f l i gh t Network and a

t o t a l of f i v e t h a t w e w i l l be able to see from e a r t h , so f i v ewe cannot and f ive we can.QUESTION: The l a s t f i v e lu na r module?McMULLEN: A l l t e n of t hose I gave were lunar moduleburnsHAGEr Transea r th i n j ec t ion bu rn is a l s o from be h indthe moon, t h e one t h a t br ings them ou t on t h e way home.McMULLEN: If you are keeping book on these, threeof t h e burns Imve you were t h e br ak in g maneuver, so w e a l lwind up w i t h numbers adding up to t h e r i g h t number of burns.O'DONNELL: Let's get one quest ion here and w e ' l l

s w i t c h t o Houston.


82/84

I 3age could g i v e usa progress TV camera that

fc t h a t we w i l l havel a s t v a l i d a t i o n t e s t

which w i l l give during countdowndemonst rat fon w t h e whole sys tem,i nc l ud i ng t h e grou nies through t h enetwork to . i t c h t o Houston now.(NO response. >

A l l r i g h t . Back re in Washington. A couple more.QUESTION: What happens to t h e , , ( Inaud i b l e )?

A r e there any more burns to t h a t to gel; it out?HAGE: I t w i l l remain in t h a t h igh e l l i p t i c a l o r b i t .

e have no way of commanding t h e descents tage once we do t h e s t a g i n g maneuver of the lunar module.

0 9 : Okay, Back here.a u d i b l e ) , . . i l l there beany o t h e r women's name on t h e moo as a r e s u l t of Apollo 101

HAGE: The procedure by which landmarks on t h e moonare off c i a l fI* .It u n o f f i c i a l l a b e l l i n g ,

rised if there a r e n ' t , b u t8.9a l t e r n a t e missions, f o ris it impossible in

raetice operations?It might be

here w e can'tquite rest don' t want to get t h e


83/84

7esrcised t h eantage of LM ope ra t ions ,

t h e Apollo 8 marginst h a t w e d i d n ' tpol10 10 are alsocause we are not

So i n f equa te Apollo 8command service module margins asequal level,

ill be ope ra t ing att h e same cons w i l l be ope ra t ingApollo 11 a t . believe t h e lowestone we ha of 10 per c e n t of t h et o t a l , but I It 's in t h a t gene ra lv i c i n i t y , We nned into the CSM fort h e landing ~ p ~ ~ ~ ~ t ehose cond i t i onsw i t h t h e Apo

iscuss in a l i t t l eade t o t h e l a n d i n gn t weigh? Ares t program or t h eyou confiden t r ans la t ab leu n i t is 8C

i f f e s of t h e changese on t h e t e s tlanding radar

s of equ iva l en tlanding radar f l y i n gof ranges t h a t ity t h i n g t h a t isairnst t h e ear th

PY t would giveU %


84/84

38l u n a r s u r f a c e t h a t m i g h t be d i f f e r e n t t ha n w e a n t i c i p a t e ,we have added e s s e n t i a l l y e l e c t r i c a l p i c k o f f s f r o m t h e fourbeams of t h e radar t h a t are f e d out on te lemet ry s y s t e m s ,and w e w i l l read t h e s i g n a t u r e t h a t comes back from t h o s efourbeams and use it a,s a means of c o r r e l a t i n g w i t h whatw e have gotten from our a i r c r a f t t e s t s .

So w e t h i n k it i s going t o be a very meaningfultes t .U

0 LL: Any more quest ions?Back here,

t h a t t h e p hase burn w a s designet o give s imi l a r itions f o r t h e rendezvous. AreMCMU w i l l wind up w i t h e s s e n t i a lt h e same f i g h t i t w i l l be o c c ur r i ng i ne s s e n t i a l l y the-- 11 wind up within posit ions t o giveu s a rendezvous essen t ia l ly above t h e same p o i n t s o n t h e l unasu r f ace , so e6 entiakllly the phasing burn coupled w i t h t h ein se r t io n burn-- A t t h e completion of t h e i n s e r t i o n b urn w eshould have cond i t i ons t a t are i d e n t i c a l t o what w e w i l l besee ing on t h e lunar Banding mission a t t h e completion of t h elaunch and i n s er t i on i n t o o r b i t from t h e l una r su r f ace .*IxIMNELL: One more.

~ ~ X S ~ ~ Q ~ :ou mentioned t h e p o s s i b i l i t y of thecommand module going t o rendezvous w i t h t h e lunar module.Does t h i s i n any way compromise your a b i l i t y t o l eave t h el u n a r , g e t the command back?GE: The service propuls ion sys tem propel lantincludes capab or t h a t kind of rescue, and t h e margins

apollo 10 briefing

Documents